Airplane motor



Jan. 17, 1928. 1,656,245

E. A. STALKER AIRPLANE MOTOR Filed May 25. 1925 m Edwa rd fi. 5mm

Patented Jan. 17, 1928.

UNITED STATES EDWARD A. STALKER, OF ANN ARBOR, MICHIGAN.

AIRPLANE MOTOR.

Application filed May 23, 1925. Serial No. 32,514.

The primary object of invention is to provide a motor of simple construction that can be cheaply manufactured and efliciently' used in an aircraft.

It is a further object of my invention to provide a motor wherein the combustible charges are forced in the combustion chamber by the aid of air from one or more air nozzles placed in the slip stream of the pro peller on the cylinder.

It is another object of my invention to provide a two cycle motor for aircrafts wherein the forcing out of exhaust gases from the cylinder chamber will be aided by the air from the propeller slip stream that enters one or more nozzles placed on the cylinder.

My motor is so designed that the axis of the above mentioned nozzle, or nozzles, are placed at an angle between plus or minus thirty degrees from the line of flight.

It is a further object of my invention to provide a converging nozzle in the cylinder that is disposed in the slipstream of the propeller so that the air therefrom will aid in both forcing the combustible mixture into the combustion chamber and after the ignition of the same will force out the exhaust gases through the exhaust port.

With the above and other objects in view, my invention consists in the arrangement, combination and construction of the various parts of my improved motor as described in the specification, claimed in my claims and shown in the accompanying drawings, in which:

Fig. 1 is a horizontal, central sectional view of a part of my improved motor.

Fig. 2 is a vertical sectional view. taken on line 22 of Fig. 1.

Fig. 3 is a front view, partly in section, of a part of my improved motor.

Fig. 4 is ahorizontal sectional view of the piston used in my improved motor showing the passages therein.

Fig. 5 is a longitudinal sectional view of the piston used in my improved device.

I have shown a crank case or engine housing having the cylinders 11 and 12 extending horizontally therefrom. Positioned in the engine housing is the crank shaft 14 to the cranks of which are fitted the connecting rods 15. A propeller 16 is secured to one end of the crank shaft 14. Attached to the ends of the rods and adapted for reciprocation in the cylinders 11 and 12 are the specially constructed pistons 17 that have i the inner walls. of th: cylinder.

Disposed on the cylinder 11 in the slip stream of the propeller is the converging nozzle 19 that has the opening 20 into the cylinder chamber 44. This nozzle 19 ispreferably placed at'an angle of between plus or minus thirty degrees from the line of the conventional rin s 18 bearing againstflight, and immediately adjacent the charm ber 44 is tilted'upwardly.

An exhaust port 21 isplaced at any part of the cylinder circumference just above the top of the piston 17 when the same has completed its down stroke. A section of the head of the cylinder protrudes outwardly as at 22, and into this portion is fitted the spark plug 23. Around the extreme end of the cylinder are also placed the fins 24 that aid in keeping the head thereof cool.

The piston 17 has the assage 25 with the top opening 26and the side openings 27 and 28 in its head. A pocket 29 that leads into the passage 25 and has the outer opening 30 is also located in the head of the piston 17.

uel is carried by the lines 31 through the needle valves 32 and 33 into the air passages 34 and 35 where the same is mixed with air ton 17 hasmoved to the downward end of its stroke to align the opening 27 and 30 with the openings 37 and 36 in the cylinder wall. 3

The air passages 34 and 35 which have the butterfly valves 38 and 39 therein terminate in the single passage 40, which is curved as at 41 to prevent the outward circulation of the fuel. The converging nozzle 42 that 7 is placed in the slip stream of the propeller 16 is attached to the end of the passage 40. This nozzle 42 may also be fed by an air line 43 from a source of air under pressurepreferably from the crank case compression.

In the practical use of my improved motor, fuel passes from the lines 31 through the needle valves 32 and 33 into the air passages 35 and 34. At this point air from the nozzle 42 is mixed with the fuel and is forced into the passage 25 and the pocket 29 when the openings 27 and 30 in the pis ton17 are aligned with the 0 min s 37 and as in the cylinder at the an of the dawn ward stroke of the pie (in the up stroke or the piston, the o n: 23 A 1th the openingso that the air l on valve 38 will be open and valve 39 will be closed, thereby forcing a rich mixture into the pocket 29 and a very lean mi: are into the passage 27'. Till ot 29 is 1 lo rted that it comes under the snarl: plu

on the top of the piston stro thus he rich as heat mixture will be easily ignited and t th refrom will burn the leaner fuel.

The exhaustgases are blown out the e:-

haust port 21, through the cylinder openi of the piston 17) by the at enters the cylinder from the opening 20 that is also opened short y alter the port 2i opened. The air will be do V i by the curvature of the ope ing- 9.0 1. cylinder so as to con'ipletely GYLl'tllhtG we... cylinder. The same action i ill occur on the out stroke of the piston, the passe 35 be ing so constructed and timed. that he fuel Will not pass from the opening 28 until the opening;- 20 and port have been closed. The air entering the cylinder chamber l ifrom the nozzle 19 also aids in cor I have described my im iroved motor as having two simple convergiu air nozzles. I desire it to be understood .t a inrl of nozzles may be used, or they (the nozzles) may be compound.

It Will be noted that in my detailed description, I have described cylinder 11 vcith its fittings, but I desire it to be understood thatcylinders 11 and 12 and the littings therefor are exactly alike in every detail. 7

It is obvious that various changes may be made in the arrangement, combination and construction of the various parts oit' my improved motor 'ithout departing from the spirit of my invention, and it my intention to cover by my claims such changes as may be reasonably included Within the scope thereof.

What I claim is:

1. In combination, a cylinder having a combustion chamber, a piston adapted for reciprocation therein, two air passages leading into said cylinder, means for supplying air to said passages, a fuel source, feed lines leading from said fuel source to said air passages, means in said piston whereby fuel is forced into said combustion chamber from said air passages when the piston reaches a predetermined position of its stroke, means for igniting said fuel and means for reciprocation therein. two air pas forcing the exhaustgases from said chamber.

In combinatiom-a cylinder having a combustion chamber, a piston adapted for reciprocation therein, two air passages having one oi. their ends leading into the cyludei' and the other ends terminating into a 'le curved pas-sage. a (ODVOlf-lllg' nozzle s cured on the end of said passage, means ting air into said passagethrough 1s, a iuel source, feed lines leading i source to said two air passages. in said piston through which fuel is forced by air into said Combustion chamber {rout said air paragon when the piston reaches a predetermined position of its stroke, means for igniting said fuel and means for forcing out the exhaustgases from said chamber.

In combination, a cylinder having a oinhustion chamber, a piston adapted for reciprocation therein, a fuel source, means n of its stroke. iiiruel, an exhaust per:

iiueijl nositio r. and a convoro inc nozzle ha:-

. j i into said chamber whereby :ri my be plied when the piston is at a predetermined position for forcing out he his. ses through said enhaul. In combination, a cylinder having a combustion chainljier, a piston adapted for reciprocation therein, tvto air passages having one of their ends leading into the cylinder and the other ends terminating into a single curved conv 'igr uo 'zlo secured on the end of said curi d passage. means lor supplying air into Fad p 'o through said nozzle, buttcrllv valves in said two iassagrcs to regulate the lion" of air therein. a fuel. source. feed lines loading from said source to said two air passages. needle valves for regulating the flow of said fuel, a fuel passage and a fuel pocket in said piston into which fuel. is forced from said air passages when the piston reaches a prede termined position of its stroke, means :for igniting said fuel and means for forcing out the exhaust from said comliuistion chamber.

5. In combination, a cylinder having? a combustion chamber. a piston adapted for are havinrr one of their ends leading into the cylinder and the other ends terminating; into a. single curved passage. a converging; nozzle secured on the end of said passage, means for supplying air into said passa e through said nozzle. a fuel source. regulated feed lines from said source to said air i sages, means in said piston for receiving); fuel haust port and a converging nozzle having an upward curved opening into the cylinder so that the cylinder may be completely evacuated of exhaust gases that are forced out by air from the nozzle.

(3. In combination, a crank case having a crankshaft positioned for rotation therein, two cylinders having combustion chambers extending horizontally from said. case, pistons adapted for reciprocation in said cylinders, rods attaching said pistons to said crankshaft so that the reciprocation of the piston will simultaneously rotate said crankshaft,a propeller fitted on one end of said crankshaft, and means for reciprocating said pistons, consisting of air passages lead ing into the cylinders, converging nozzles secured to the end of said passages and placed on said cylinder in the slipstream of said propeller, a fuel source, feed lines from said source to said. passages, means in said pistons for receiving fuel from said air passages when the pistons reach. a predeterminedposition of their stroke, means for igniting said fuel, exlie ports and converging nozzles disposed in the slipstream of said propeller, having a curved opening into the cylinders so that the cylinders may be C0111 letel evacuated of exhaust 'ases that are forced out through the said ports by air from the nozzles.

7. A device as set forth in claim 6 Wherein the converging nozzles,therein mentioned, are placed on the cylinders at an angle of between plus or minus thirty degrees from the aris'of said propeller, so that the rotary velocity of the slipstream caused by the propeller can be efficiently used.

8. In combination a cylinder having a combustion chamber, a piston adapted for reciprocation therein, a fuel source, a spark plug placed in said cylinder adjacent the head thereof for igniting the fuel in said combustion chamber, a fuel pocket having an opening adapted to pass said spark plug near the end of the outward stroke of said piston, a fuel passage in said piston, means for forcing fuel from said source into said pocket and also through said passage into said combustion chamber when the piston reaches a pre-determined position of its stroke and a converging nozzle positioned on said cylinder and having an opening into said combustion chamber for forcing out the exhaust gases from said chamber after the fuel has been ignited. by said spark plug.

9. A construction as set forth in claim 8 wherein the passage in said piston is curved laterally so that the same substantially reverses itself in direction and the opening thereof into the combustion chamber is in the top of the piston head.

10. In combination, a cylinder having a combustion chamber, a piston adapted for reciprocation in the cylinder, a fuel source, a converging nozzle on the cylinder adapted to receive fuel from said source and pass it to the combustion chamber, means for ignit ing said fuel and a converging nozzle through which air may be drawn to force exhaust gases from the chamber.

11. A construction as set forth in claim 10, wherein one end of the piston is secured to a crankshaft, a re eller is mounted on the crankshaft, and t e nozzles are positioned at an angle of plus orminus thirty degrees from the axis of the propeller and in the slipstream thereof. I

EDWARD A. STALKER. 

